CN104317306B - Satellites formation reconstructing method - Google Patents
Satellites formation reconstructing method Download PDFInfo
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- CN104317306B CN104317306B CN201410589892.3A CN201410589892A CN104317306B CN 104317306 B CN104317306 B CN 104317306B CN 201410589892 A CN201410589892 A CN 201410589892A CN 104317306 B CN104317306 B CN 104317306B
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Abstract
A kind of satellites formation reconstructing method, its key step for adjusting formation Satellite transfer track includes：Determine the original position and final position of each satellite during formation reconfiguration；Different conditions when reaching final position for satellite form corresponding transfer orbit using puppet spectrum algorithm；Form the fuel consumption control signal of the corresponding satellite microthruster of track；The transfer orbit that can be collided is filtered by discrete particle cluster algorithm；According to constraints, each Satellite Orbit Maneuver transition strategy set up in restructuring procedure；Form the control signal strategy of fuel consumption when restructuring procedure Satellite becomes rail.The present invention forms the dual layer resist of team of team Satellite transfer orbit, calculates the fuel optimal objective value of each satellite microthruster in formation reconfiguration, and then form final reconstruct track scheme.
Description
Technical field
It is more particularly to a kind of to be used for multiple satellite vector thrusts the present invention relates to a kind of satellite vector thrust control method
Control method.
Background technology
Micro-gastric carcinoma flight is different from the fixed signses flight of several satellite compositions, and every satellite is all one complete
The organic composition of function.Because the change of task step, Technique performance parameter etc. is, it is necessary to carry out the reconstruct of formation form.Due to compiling
The satellite of team's flight is an organic whole in function and control, and another new formation structure is transformed to from original formation configuration
Type, the control of each Satellite Formation Flying must be mutually coordinated, could realize the allomeric function formed into columns.
The bottom control method of reconfiguration can be divided into two classes：It is based on momentum control and (continuous based on continuous microthrust
Microthrust or many momentums) control.Wherein, the control based on continuous low thrust has many advantages, such as stable, precision is high, micro- at present
Thruster is more and more applied in Spacecraft Control.Based on the formation reconfiguration of continuous microthrust, plan or calculate first
The relative motion transfer track of optimization, then realizes transfer process with tracking and controlling method.Formation reconfiguration not only wants every satellite
Complete corresponding Orbit Transformation, in addition it is also necessary to consider the cooperative motion between formation Satellite, limited to by existing control technology, also
Reliable collaborative can not be accomplished, and then meet the constraint of the globality performance indications in restructuring procedure.
The content of the invention
It is an object of the invention to provide a kind of satellites formation reconstructing method, solve in satellites formation restructuring procedure, satellite by
The setting control of starting point to the end track is unable to the technical problem of reliable collaborative.
The satellites formation reconstructing method of the present invention, its key step for adjusting formation Satellite transfer track includes：
Determine the original position and final position of each satellite during formation reconfiguration；
Different conditions when reaching final position for satellite form corresponding transfer orbit using puppet spectrum algorithm；
Form the fuel consumption control signal of the corresponding satellite microthruster of track；
The transfer orbit that can be collided is filtered by discrete particle cluster algorithm；
According to constraints, each Satellite Orbit Maneuver transition strategy set up in restructuring procedure；
Form the control signal strategy of fuel consumption when restructuring procedure Satellite becomes rail.
The original position and the determination step of final position include：
Step 1：Point set and terminal collection are generated.Satellite and championship are numbered, satellite number i, i=1 ..., m, star
Bit number j, j=1 ..., n, m≤n, point set i-th bit has been positioned over by satellite i position and speed, by championship j desired positions
Terminal collection jth position is positioned over speed.
The step of discrete particle cluster algorithm, includes：
Step 2：Particle swarm parameter is set.Particle dimension Dim is set as 3m+3, particle scale xSize, maximum iteration
MaxIt, inertia weight w, acceleration constant c1And c2Can as needed depending on；
Step 3：When population is initialized, when population is initialized, 1~n natural number arrangement is generated at random.I-th bit
Natural number j represents that satellite i will be assigned to championship j, by preceding m of arrangement be assigned to particle in population preceding m, represents position
Put, reconfiguration scheme information is contained in so each particle；Arranged for 1~m of random generation natural number m+1~2m positions of particle
Row, represent speed；2m+1~3m positions of particle are optimal location；3m+1 of particle are adaptive optimal control angle value；The of particle
3m+2 are current fitness values, that is, energy consumption values；3m+3 of particle are Boolean type variable, when in reconfiguration scheme
When the distance between any two stars are less than minimum range, by the position 0, otherwise the position is 1；
Step 4：The positional information in particle is read, using in the energy expenditure and numerical procedure of pseudo- spectrometry numerical procedure
The distance between two stars of meaning, if the distance between any two stars are less than minimum range, terminate computing and by particle most
Latter position 0；Otherwise, the energy expenditure for calculating the program is assigned to the penultimate of particle；
Step 5：More new position and speed, judge whether to meet iterated conditional, if meeting, terminate；If it is not satisfied, then after
Continuous iteration；
Step 6：After iteration terminates, the particle that identifier is set to 0 is deleted；
Step 7：Select optimum individual and optimal value.Optimum individual is satellite and the optimum distributing scheme of phase, optimal
Value is minimal energy consumption value.
The dual layer resist of team of the satellites formation reconstructing method formation team Satellite transfer orbit of the present invention, first to single micro-
The control signal vector of thruster is optimized, and is generated for every satellite in formation from specified starting point to a plurality of of specified terminal
Fuel optimal policy or mobile nearly excellent track, higher transfer precision can be obtained with less control node, then, by respectively defending
The transfer orbit and fuel optimal policy of star, calculate the fuel optimal objective value of each satellite microthruster in formation reconfiguration, enter
And form final reconstruct track scheme.
Embodiments of the invention are described further below in conjunction with the accompanying drawings.
Brief description of the drawings
Fig. 1 is the improvement discrete particle cluster algorithm in satellites formation reconstructing method of the present invention for being cooperateed between Satellite of forming into columns
Carry out particle arrangement and structural representation during data processing.
Embodiment
In the present embodiment, every satellite is not only set to complete corresponding Orbit Transformation process based on satellites formation reconstruct, also
Need to consider the cooperative motion between Satellite Formation Flying, there is determination and uncertain for the satellite last current state of different reconstruct tracks
Situation, to the transfer orbit of each satellite in formation and correspondence microthruster fuel consumption strategy, respectively from satellite path layer and
Satellite collaborative party pattern layer is controlled signal optimization, realizes the reconfiguration scheme that energy expenditure is most saved.First, by improved discrete grain
Swarm optimization is responsible for generating the track scheme of each satellite in restructuring procedure, then, is calculated by pseudo- spectrometry in every kind of track scheme
The energy input of each satellite correspondence microthruster is calculated, and finally, is determined by improved discrete particle cluster algorithm collisionless optimal heavy
Structure process transfer orbit scheme.
The track optimizing of single spacecraft is completed by (Gauss) puppet spectrum algorithm, by with the quantity of state of time consecutive variations and
Controlled quentity controlled variable is discrete in limited time point progress, with Lagrange interpolation polynomials approximate expression quantity of state and control on discrete point
Flow function, recycles Gauss numerical integrations that integral constraint is converted into algebraically summation constraint, most optimal control problem is converted at last
Solved for NLP problems, several fuel optimal policies or the movement of single spacecraft are obtained using the good characteristic of pseudo- spectrum algorithm
Nearly excellent track.
Path planning is reconstructed by improving particle cluster algorithm, filtering has the satellite reconstruct track of collision, formed many
Individual nearly excellent scheme, and optimal reconfiguration scheme is selected according to formation constraints.
Discrete particle cluster algorithm is improved as follows：
The position of particle：Random mutually different sequence of natural numbers of the generation no more than m represents position X=(x1,x2,…,
xm), 1≤i≤m, 1≤xi≤ m, represents a kind of scheme, xiRepresent satellite x in this scenarioiCorresponding to championship i；
The speed of particle：Random mutually different sequence of natural numbers of the generation no more than m represents speed V=(v1,v2,…,
vm), 1≤i≤m, 1≤vi≤ m, represents a turnaround sequence, viValue correspondence exchangeable object position.With V=(2,6,3,5,
4,1) exemplified by, the conversion process that it is represented as：
①ν1=2, represent x1And x2Exchange；
②v2=6, represent x2And x6Exchange；
③v3=3, represent x3And x3Exchange, i.e., do not exchange；
④v4=5, represent x4And x5Exchange；
⑤v5=4, represent x5And x4Exchange；
⑥v6=1, represent x6And x1Exchange；
Now V represents the exchange process of 6 times.
The addition rule of Position And Velocity：Position And Velocity is added and obtains a new position,
Expressed by the formula is：If viX if=iiKeep constant, otherwise xiWith xviExchange.The turnaround sequence is from the 1st
Position is swapped successively to m, is exchanged m times altogether, produces a new position.
For example, position X=(1,2,3,4,5,6), speed V=(2,6,3,5,4,1), then X+V exchange obtain new position
Put X=(1,6,3,4,5,2).
The key step of the present embodiment satellites formation reconstructing method is as follows：
Step 1：Point set and terminal collection are generated.Satellite and championship are numbered, satellite number i, i=1 ..., m, star
Bit number j, j=1 ..., n, m≤n, point set i-th bit has been positioned over by satellite i position and speed, by championship j desired positions
Terminal collection jth position is positioned over speed.
Step 2：Particle swarm parameter is set.Particle dimension Dim is set as 3m+3, particle scale xSize, maximum iteration
MaxIt, inertia weight w, acceleration constant c1And c2Can as needed depending on.
Step 3：Population is initialized, when population is initialized, and 1~n natural number arrangement is generated at random.I-th bit from
So number j represents that satellite i will be assigned to championship j, by preceding m of arrangement be assigned to particle in population preceding m, represents position,
Contain reconfiguration scheme information in so each particle；M+1~2m positions of particle are 1~m of random generation natural number arrangement, table
Show speed；2m+1~3m positions of particle are optimal location；3m+1 of particle are adaptive optimal control angle value；3m+2 of particle
It is current fitness value, that is, energy consumption values；3m+3 of particle are Boolean type variable, when in reconfiguration scheme any two
When the distance between star is less than minimum range, by the position 0, otherwise the position is 1.Specific particle alignment structure is as shown in Figure 1.
Step 4：The positional information in particle is read, using in the energy expenditure and numerical procedure of pseudo- spectrometry numerical procedure
The distance between two stars of meaning, if the distance between any two stars are less than minimum range, terminate computing and by particle most
Latter position 0；Otherwise, the energy expenditure for calculating the program is assigned to the penultimate of particle；
Step 5：More new position and speed, judge whether to meet iterated conditional, if meeting, terminate；If it is not satisfied, then after
Continuous iteration.
Step 6：After iteration terminates, the particle that identifier is set to 0 is deleted；
Step 7：Select optimum individual and optimal value.Optimum individual is satellite and the optimum distributing scheme of phase, optimal
Value is minimal energy consumption value.
The satellites formation reconstructing method formation Bilevel programming step of the present embodiment, i.e., high-rise planning passes through discrete particle cluster
Optimal reconfiguration scheme realizes the fuel optimal objective formed into columns；Low layer planning is using pseudo- spectrometry, on the premise of constraints is met,
Generate that a plurality of fuel from specified starting point to specified terminal is optimal or nearly excellent track for every satellite in formation.When low layer planning
After calculating is finished, result is fed back into high-rise planner, high-rise planner finally determines reconfiguration scheme.
Embodiment described above is only that the preferred embodiment of the present invention is described, not to the model of the present invention
Enclose and be defined, on the premise of design spirit of the present invention is not departed from, technical side of the those of ordinary skill in the art to the present invention
In various modifications and improvement that case is made, the protection domain that claims of the present invention determination all should be fallen into.
Claims (1)
1. a kind of satellites formation reconstructing method, its key step for adjusting formation Satellite transfer track includes：
Determine the original position and final position of each satellite during formation reconfiguration；
Different conditions when reaching final position for satellite form corresponding transfer orbit using puppet spectrum algorithm；
Form the fuel consumption control signal of the corresponding satellite microthruster of track；
The transfer orbit that can be collided is filtered by discrete particle cluster algorithm；
According to constraints, each Satellite Orbit Maneuver transition strategy set up in restructuring procedure；
Form the control signal strategy of fuel consumption when restructuring procedure Satellite becomes rail；
The original position and the determination step of final position include：
Step 1：Point set and terminal collection have been generated, satellite and championship have been numbered, satellite number i, i=1 ..., m, championship are compiled
Number j, j=1 ..., n, m≤n, have been positioned over point set i-th bit, by championship j desired positions and speed by satellite i position and speed
Degree is positioned over terminal collection jth position；
The step of discrete particle cluster algorithm, includes：
Step 2：Particle swarm parameter is set, and particle dimension Dim is set as 3m+3, particle scale xSize, maximum iteration
MaxIt, inertia weight w, acceleration constant c1And c2Can as needed depending on；
Step 3：Population is initialized, when population is initialized, and 1~n natural number arrangement, the natural number j of i-th bit are generated at random
Represent that satellite i will be assigned to championship j, by preceding m of arrangement be assigned to particle in population preceding m, represent position, it is so every
All contain reconfiguration scheme information in individual particle；M+1~2m positions of particle are 1~m of random generation natural number arrangement, represent speed
Degree；2m+1~3m positions of particle are optimal location；3m+1 of particle are adaptive optimal control angle value；3m+2 of particle are to work as
Preceding fitness value, that is, energy consumption values；3m+3 of particle are Boolean type variable, when any two stars in reconfiguration scheme
The distance between when being less than minimum range, by the position 0, otherwise the position is 1；
Step 4：The positional information in particle is read, using in the energy expenditure and numerical procedure of pseudo- spectrometry numerical procedure any two
The distance between star, if the distance between any two stars are less than minimum range, terminate computing and by particle last
Position 0；Otherwise, the energy expenditure for calculating the program is assigned to the penultimate of particle；
Step 5：More new position and speed, judge whether to meet iterated conditional, if meeting, terminate；If it is not satisfied, then continuing to change
Generation；
Step 6：After iteration terminates, the particle that identifier is set to 0 is deleted；
Step 7：Optimum individual and optimal value are selected, optimum individual is satellite and the optimum distributing scheme of phase, and optimal value is
For minimal energy consumption value.
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105138010B (en) * | 2015-08-31 | 2017-07-28 | 哈尔滨工业大学 | A kind of distributed finite time tracking controller design method of Satellite Formation Flying |
| CN106681138B (en) * | 2016-12-02 | 2019-06-21 | 上海航天控制技术研究所 | A kind of balanced in-orbit implementation method of Satellite Formation Flying system fuel consumption |
| CN107554817B (en) * | 2017-07-11 | 2020-02-14 | 西北工业大学 | Satellite composite formation method |
| CN107885917A (en) * | 2017-10-27 | 2018-04-06 | 中国地质大学（武汉） | Become satellite constellation reconstructing method, equipment and the storage device of rail strategy based on antarafacial |
| CN108216687B (en) * | 2017-12-25 | 2019-12-20 | 中国空间技术研究院 | GEO satellite orbit-changing strategy calculation method, system and medium based on particle swarm optimization |
| CN110488858B (en) * | 2018-09-27 | 2020-05-19 | 北京航空航天大学 | Method for reconstructing formation flight low thrust by adopting Jordan decomposition |
| CN110083170A (en) * | 2019-04-11 | 2019-08-02 | 北京航空航天大学 | A kind of optimal control method carrying out track holding using solid micro-thruster |
| CN113110560B (en) * | 2021-05-24 | 2021-12-07 | 四川大学 | Satellite formation reconstruction model prediction control method based on Chebyshev inequality |
| CN113296535B (en) * | 2021-05-24 | 2022-06-21 | 四川大学 | Satellite formation reconstruction algorithm based on stochastic model predictive control |
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